The third phase of a program to develop understanding of and tolerance-level criteria for the deleterious effects of electro-static rocket exhaust (Cs, Cs(+), Hg, Hg(+)) and materials of rocket construction impinging on typical classes of spacecraft (S/C) surfaces was completed. Models of ion engine effluents and models describing the degradation of S/C surfaces by these effluents are presented. Experimental data from previous phases are summarized and Phase 2 data and analysis are presented in detail. The spacecraft design implications of ion engine contami-nants are discussed. (Author)
Electrostatic Propulsion Beam Divergence Effects on Spacecraft Surfaces, Volume 2
1973
205 pages
Report
Keine Angabe
Englisch